Bleed system driven in simplified manner for a turbojet or turboprop engine

Abstract

A bypass gas turbine engine having an intermediate structural casing positioned between a primary flow path and a bypass flow path, and configured between a low pressure compressor and a high pressure compressor. The engine further having a bleed device arranged to deflect a portion of a gas flow from the low pressure compressor toward the bypass flow path. The bleed device includes an annular cavity defining a manifold situated upstream the intermediate casing and opening along the outer wall of the primary flow path, a plurality of conduits positioned along the intermediate casing, a plurality of tubes configured around the high pressure compressor and connecting the conduits to the bypass flow path, and at least one flow regulating valve disposed along the interior of each of the plurality of tubes.

We claim:  
     
       1. A bypass gas turbine engine for an aircraft having an intermediate structural casing ( 9 ) positioned between a primary flow path ( 2 ) bounded by inner and outer walls and a bypass flow path ( 3 ), and axially configured between a low pressure compressor ( 5 ) and a high pressure compressor ( 7 ), said engine further having a bleed device arranged to deflect a portion of a gas flow from the low pressure compressor ( 5 ) toward the bypass flow path ( 3 ), said bleed device comprising: 
       an annular cavity ( 16 ) defining a manifold situated upstream said intermediate casing ( 9 ) and opening along the outer wall of the primary flow path ( 2 ), said manifold permanently communicating with said primary flow path ( 2 );  
       a plurality of conduits ( 18 ) substantially axially aligned with a central axis of said engine and positioned along the intermediate casing ( 9 ), said plurality of conduits connecting to said manifold ( 16 );  
       a plurality of tubes ( 20 ) configured around the high pressure compressor ( 7 ) and connecting said conduits ( 18 ) to the bypass flow path ( 3 ); and  
       at least one flow regulating valve ( 22 ) disposed along the interior of each of said plurality of tubes and cooperating therewith to regulate the gas flow disposed therein.  
     
     
       2. The bypass gas turbine engine according to  claim 1  wherein the intermediate casing ( 9 ) and the conduits ( 18 ) constitute a single, integral unit and being manufactured by casting or welding. 
     
     
       3. The bypass gas turbine engine according to  claim 1  or  2  wherein the intermediate casing ( 9 ) includes a plurality of radial arms ( 15 ) configured such that the conduits ( 18 ) are positioned along a circumferential space separating adjacent ones of said radial arms ( 15 ) extending towards an outer annular portion ( 9   a ) of said intermediate casing ( 9 ). 
     
     
       4. The bypass gas turbine engine according to  claim 1  wherein the manifold ( 16 ) communicates with the primary flow path via an inducer having a plurality of orifices defined along the outer wall of the primary flow path. 
     
     
       5. The bypass gas turbine engine according to  claim 1  wherein the flow regulating valves are adjustable within each of said plurality of tubes in dependently from one another.